# TCDS A27CE: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 18
- Revised: October 11, 2007
- Product: Aircraft, Small/Large Airplane
- Certification basis: Part 23, Part 25
- Registered aircraft: 223, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/5b/35/5b355465e706a7f3ee8f67d05734432e7e606a9b65471cab1cf2fb53ad945b66
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CD6DBCFFEE6F70ED86257ED7005D8575.0001
- Page: https://openairdocs.org/tcds/A27CE

## Models (2)

As the data sheet lists them.

- 551
- 501

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 
Rev. No. 18 14 11 13 11 14 17 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 A27CE  
 Revision 18  
 Textron Aviation Inc.  
501 
551  
 
 July 29, 2015  
 
TYPE CERTIFICATE DATA SHEET NO. A27CE 
 
This data sheet which is part of Type Certificate No. A27CE prescribes conditions and limitations under which the product for  
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.  
 
Type Certificate Holder Textron Aviation Inc. 
   One Cessna Boulevard 
   Wichita, Kansas  67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to 
   Textron Aviation Inc. on July 29, 2015 
 
I. Model 501, Citation (Normal Category), Approved January 7, 1977 
 
 Engines  Two Pratt & Whitney Aircraft of Canada, Ltd. JT15D-1A or JT15D-1B turbofans used in 
any combination (See Note 13).  
    
 Fuel  Commercial kerosene Jet A, Jet A-1, Jet A-2, Jet B, JP-4, JP-5 or JP-8.  These fuels,  
   except Military JP-4, JP-5 and JP-8, require addition of anti-ice additive (Phillips  
   PFA55MB, MIL-I-27686D or MIL-I-27686E) and must be blended into the aircraft fuel  
   in concentrations not less than 0.060 percent or more than 0.15 percent by volume.  For  
   emergency use of aviation gasoline and fueling procedures, refer to Airplane Flight  
   Manual. 
 
 Engine Limits  Static thrust standard day, sea level: 
 
    Takeoff (5 min.)   2200 lb. 
    Max. continuous   2090 lb. 
 
   Max. permissible engine rotor operating speeds: 
    N1 (Fan) JT15D-1A 102.1 percent  16,336 r.p.m. 
    N1 (Fan) JT15D-1B 102.1 percent  16,336 r.p.m. 
       below 30,000 ft. 
    N1 (Fan) JT15D-1B 103.4 percent  16,540 r.p.m. 
       30,000 ft. and above 
    N2 (Gas Gen.) 95 percent  31,120 r.p.m. 
   Max. permissible interturbine gas temperatures: 
    Takeoff   700° C. 
    Max. continuous   680° C. 
    Transient (starting 2 Sec.)  700° C.

A27CE 2 Rev. 18 
 
I. Model 501  (cont’d) 
 
 Airspeed Limits (CAS) VMO  (Maximum operating) 
    Sea level to 14,000 ft.   260 knots 
    14,000 ft. to 28,000 ft.   275 knots* 
   MMO 
    Above 28,000 ft.   0.70 Mach 
   VA (Sea level) 
    11,850 lb.   182 knots 
    See AFM for variations with weight and altitude and optional configurations 
   VSB (Speed for maximum gust intensity)  210 knots 
   VFE (Flaps extended) 
    40° (Landing)   174 knots 
    15° (Takeoff and approach)  200 knots 
   VMCA (Minimum control speed) Air  Below stall speed for all weights 
   VMCG (Minimum control speed) Ground  55 knots 
   VLO  (Landing gear operating)  174 knots 
   VLE  (Landing gear extended)  174 knots 
   VSB  (Speed brakes extended) Any speed with or without flaps 
 
   *See NOTE 6 for restricted VMO for optional fuel weight configuration 
 
 C.G. Range (Landing (+246.4 in.) to (+255.9 in.) at 7,500 lb. or less (18-30 percent MAC) 
  Gear Extended) (+250.0 in.) to (+255.9 in.) at 11,850 lb. (22.6-30 percent MAC) 
   Variation is linear between points 
 
 Empty Wt. C.G. Range None 
 
 MAC  79.61 in. (L.E. of MAC at Sta. +232.04) 
   Note this is reference MAC for basic wing without tip 
 
 Maximum Weight Takeoff  11,850 lb. 
   Landing  11,350 lb. 
   Zero fuel*  8,400 lb. 
   Ramp  12,000 lb. 
   *See NOTE 6 for optional zero fuel weights 
 
 Minimum Crew For all flights:  one pilot plus equipment specified in the Airplane Flight Manual, or two  
   pilots 
 
 No. of Seats  Maximum of nine (See Aircraft Weight and Balance Manual for optional seating  
   arrangements) 
 
 Maximum Baggage Nose compartment  350 lb. (at Sta. + 74.0) 
   Aft cabin  650 lb. (at Sta. +286.3) 
 
 Fuel Capacity (Gal.) Two wing tanks:  Total 287 each; usable 282 each 
     ARM = +256.0 in. 
   See NOTE 1 for data on unusable fuel 
 
 Oil Capacity (Gal.) Two engine mounted tanks:  Total 2.14 each; usable 1.25 each 
     ARM = +322.0 in. 
   See NOTE 1 for data on undrainable oil 
 
 Maximum Operating 41,000 ft. 
  Altitude

Rev. 18 3 A27CE 
 
I. Model 501  (cont’d) 
 
 Control Surface Elevator Up 20° +1° Down 15° +1° 
  Movements  Elevator trim tab Up 10° +1° Down 19° +1° 
   Rudder Right 22° +1° Left 22° +1° 
    (perpendicular to hinge) 
   Rudder trim tab Right 10° +1° Left 10° +1° 
    (perpendicular to hinge) 
   Aileron Up 21° from neutral 
       Down 16° from neutral 
    (rig neutral 2° down) 
   Aileron trim tab Up 20° from neutral 
       Down 20° from neutral 
   Wing flap   Down 0° to 40° +1° 
   Speed brake - Upper Up 0° to 58° +2° 
   See Airplane Maintenance Manual or Cessna Dwg. 5500003 for rigging tolerances 
 
 Serial Nos. Eligible 501-0001 and on 
 
II. Model 551, Citation II (Normal Category), Approved June 30, 1978 
 
 Engines  Two Pratt and Whitney Aircraft of Canada, Ltd. JT15D-4 turbofans 
 
 Fuel  Commercial kerosene Jet A, Jet A-1, Jet A-2, Jet B, JP-4, JP-5 or JP-8.  These fuels,  
   except Military JP-4, JP-5 and JP-8, require addition of anti-ice additive (Phillips  
   PFA55MB, MIL-I-27686D or MIL-I-27686E) and must be blended into the aircraft fuel  
   in concentrations not less than 0.060 percent or more than 0.15 percent by volume.  For  
   emergency use of aviation gasoline and fueling procedures, refer to Airplane Flight 
   Manual. 
 
 Engine Limits  Static thrust standard day, sea level: 
 
    Takeoff (5 min.)   2500 lb. 
    Max. continuous   2375 lb. 
 
   Max. permissible engine rotor operating speeds: 
    N1 (Fan) JT15D-4 104 percent  16,540 r.p.m. 
    N2 (Gas Gen.) 96 percent  31,450 r.p.m. 
   Max. permissible interturbine gas temperatures: 
    Takeoff   700° C. 
    Max. continuous   680° C. 
    Transient (starting 2 sec.)  700° C. 
 
 Airspeed Limits (CAS) VMO (Maximum operating) 
    Sea level to 14,000 ft.   260 knots 
    14,000 ft. to 28,000 ft.   275 knots* 
    Sea level to 30,500 ft.  260 knots 
      (S/N 551-0550 and up) 
   MMO  Above 28,000 ft.   0.70 Mach 
   VA  (Sea level)   181 knots 
    12,500 lb. 
    See AFM for variations with weight and altitude and optional configurations 
   VSB (Speed for max. gust intensity)  210 knots 
   VFE (Flaps extended) 
    40° (Landing)   174 knots 
    15° (Takeoff and approach)  200 knots 
   VMCA (Minimum control speed) Air  75 knots 
   VMCG (Minimum control speed) Ground  62 knots 
   VLO  (Landing gear operating)  174 knots 
   VLE  (Landing gear extended)  174 knots 
   VSB  (Speed brakes extended) Any speed with or without flaps 
   *See NOTE 6 for restrictive VMO for optional fuel weight configuration, S/N 551-0001  
   through 551-0549

A27CE 4 Rev. 18 
 
II. Model 551  (cont’d) 
 
 C.G. Range (Landing (+276.1 in.) to (+285.8 in.) at 8,540 lb. or less (18-30 percent MAC) 
  Gear Extended) (+279.2 in.) to (+285.8 in.) at 12,500 lb. or less (22.6-30 percent MAC) 
   Variation is linear between points 
 
 Empty Wt. C.G. Range None 
 
 MAC  80.98 in. (L.E. of MAC at Sta. +261.56) 
   Note this is reference MAC for basic wing without tip 
 
 Maximum Weight Takeoff   12,500 lb. 
   Landing   12,000 lb. 
   Zero fuel*  9,500 lb. (S/N 551-0001 through 551-0549) 
      11,000 lb. (S/N 551-0550 and up) 
   Ramp   12,700 lb. 
   *See NOTE 6 for optional zero fuel weight (S/N 551-0001 through 551-0549) 
 
 Minimum Crew For all flights:  one pilot plus equipment specified in the Airplane Flight Manual, or two  
   pilots 
 
 No. of Seats  Maximum of eleven (See Aircraft Weight and Balance Manual for optional seating  
   arrangements) 
 
 Maximum Baggage Nose compartment  350 lb. (at Sta. + 74.0) 
   Aft cabin  400 lb. (at Sta. +321.0) 
      200 lb. (at Sta. +338.0) 
   Tailcone  200 lb. (at Sta. +442.0) 
 
 Fuel Capacity (Gal.) Two wing tanks:  Total 376 each; usable 371 each 
     ARM = +285.9 in. 
   See NOTE 1 for data on unusable fuel 
 
 Oil Capacity (Gal.) Two engine mounted tanks:  Total 2.08 each; usable 1.50 each 
     ARM = +367.0 in. 
   See NOTE 1 for data on undrainable oil 
 
 Maximum Operating 43,000 ft. 
  Altitude 
 
 Control Surface Elevator Up 20° +1° Down 15° +1° 
  Movements  Elevator trim tab - S/N 551-0001 through S/N 551-0576 
     Up 15° +1°, -0° Down 17° +1°, -0° 
   Elevator trim tab - S/N 551-0577 and up 
     Up 17° +1°, -0° Down 15° +1°, -0° 
   Rudder Right 22° +1° Left 22° +1° 
    (perpendicular to hinge) 
   Rudder trim tab Right 10° +1° Left 10° +1° 
    (perpendicular to hinge) 
   Aileron Up 19° +1° Down 15° +1° 
   Aileron trim tab Up 20° +1° Down 20° +1° 
   Wing flap   Down 0° to 40° +1° 
   Speed brake - Upper Up 0° to 58° +2° 
 
   See Airplane Maintenance Manual for rigging instructions 
 
 Serial Nos. Eligible 551-0001 and on

Rev. 18 5 A27CE 
 
Data Pertinent to All Models 
 
Datum  94.0 in. forward of the front face of the forward pressure bulkhead which is station 
+94.0. 
 
Leveling Means  Seat rails 
 
Certification Basis:  
Model 501 
Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 through 23-16 except as follows: 
Delete Paragraphs 23.45 through 23.77, 23.831, 23.1091(c)(2), 23.1303, 23.1323, 23.1441 through 23.1449, 23.1581 through 
23.1583(f), 23.1583(h) through 23.1587; Add Paragraph 23.1385 as amended through 23-20, and from Part 25 of the Federal 
Aviation Regulations effective February 1, 1965, as amended by 25-1 through 25-17, Paragraphs 25.1195, 25.1199 and 25.1203; 
as amended by 25-1 through 25-37, Paragraphs 25.101 through 25.125, 25.831, 25.934, 25.1091(d)(2), 25.1197, 25.1201, 
25.1303, 25.1305(a)(7), 25.1323, 25.1439 through 25.1453, 25.1581 through 25.1583(c)(3), 25.1583(e) through 25.1587; Part 36 
of the Federal Aviation  Regulations effective December 1, 1969, as amended by 36-1 through 36-5; SFAR 27, fuel venting. 
 
Equivalent safety items 
(1) Ground Loads  FAR 23.471 through 23.511 
(2) Landing Gear  FAR 23.723 through 23.727 
(3) Retracting Mechanism FAR 23.729(e) 
(4) Wheels, Tires and Brakes FAR 23.731 through 23.735 
(5) Engine Rotation FAR 23.903(e)(2) 
(6) Fuel System Icing FAR 23.951(c) 
(7) Fuel System Check Valves FAR 23.995(f) 
(8) Oil Strainer Indicator FAR 23.1019(a)(3) 
(9) Flight Director Disconnect FAR 23.1335 
(10) Airspeed Indicator Markings FAR 23.1545 
(11) Maneuvering Speed Placard FAR 23.1563(a) 
(12) Protective Breathing Equipment FAR 25.1439(b) 
 
Note: Compliance with Special Conditions No. 25-25-CE-4 dated June 10, 1970, has been shown. 
 
Model 551 
Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 through 23-16 except as follows:  
Delete Paragraphs 23.21 through 23.31, 23.45 through 23.77, 23.157, 23.171 through 23.177, 23.251, 23.345, 23.351, 23.361, 
23.471 through 23.511, 23.571, 23.572, 23.629, 23.679, 23.723 through 23.737, 23.773, 23.775, 23.777, 23.783, 23.807, 23.831,  
23.903(c), 23.1091(c)(2), 23.1301, 23.1303, 23.1307, 23.1309, 23.1321, 23.1323, 23.1325, 23.1385(c), 23.1435, 23.1441 through 
23.1449, 23.1581 through 23.1583(f), 23.1583(i) through 23.1587.  Add Paragraphs 23.1143(e) and 23.1385(c) as amended 
through 23-18 and 23.1301 and 23.1335 as amended through 23-20; and from Part 25 of the Federal Aviation Regulations 
effective February 1, 1965, as amended by 25-1 through 25-17, Paragraphs 25.812, 25.863, 25.1195, 25.1199, 25.1203, 25.1309, 
and 25.1435; as amended by 25-1 through 25-37, Paragraphs 25.21 through 25.31, 25.101 through 25.125, 25.147(c)(e), 25.171 
through 25.177, 25.251, 25.305(c), 25.345, 25.351, 25.361, 25.471 through 25.511, 25.571, 25.573, 25.629, 25.679, 25.721 
through 25.737, 25.773, 25.775, 25.777, 25.783, 25.807, 25.831, 25.851, 25.903(b)(d), 25.934, 25.1091(d)(2), 25.1189(g)(h), 
25.1197, 25.1201, 25.1303, 25.1305(a)(7), 25.1305(c)(4), 25.1307, 25.1321, 25.1323, 25.1325, 25.1439 through 25.1453, 
25.1581 through 25.1583(c)(3), 25.1583(f) through 25.1587, and Paragraphs 25.901(c), 25.903(e)(3), and 25.1351(d) as amended 
through 25-41; Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36-6; 
SFAR 27, as amended by 27-1 through 27-3, fuel venting. For the Bendix EFS-10, Sperry EDZ-600, Sperry EDZ-601, and 
Sperry EDZ-603 Electronic Flight Instrument Systems only, compliance has been shown with the following regulations:  FAR 
25.1301, 25.1303(b), 25.1322 as amended through 25.38; FAR 25.1309, 25.1321(a), (b), (d), and (e), 25.1331, 25.1333, 25.1335 
as amended through 25-41. 
 
Equivalent Safety Items 
(1) Stall Warning  FAR 23.207(c) 
(2) Engine Rotation FAR 23.903(e)(2) 
(3) Fuel System Icing FAR 23.951(c) 
(4) Fuel System Check Valve FAR 23.995(f) 
(5) Oil Strainer Installation FAR 23.1019(a)(3) 
(6) Airspeed Indicator Markings FAR 23.1545 
(7) N2 Indicator Markings FAR 23.1549(a)(b) 
(8) Maneuvering Speed Placard FAR 23.1563(a) 
(9) Clear Vision  FAR 25.773(b)(2) 
(10) Emergency Exit Ditching FAR 25.807(d) 
(11) Fire Bottle Pressure Relief Valve FAR 25.1199(b)(c)

A27CE 6 Rev. 18 
 
(12) Protective Breathing Equipment FAR 25.1439(b)

Rev. 18 7 A27CE 
 
Data Pertinent to All Models  (cont’d) 
 
Certification Basis  (cont’d) 
 
Model 551 (cont’d) 
Note: Where applicable FAR 25 requirements reference other FAR 25 requirements, the corresponding FAR 23 requirement 
should be substituted unless the referenced FAR 25 requirement is included in the certification basis, or there is no corresponding 
FAR 23 requirement. 
 
Compliance with ice protection has been demonstrated in accordance with FAR 23.1419. 
 
Application for Type Certificate dated November 12, 1976.  Type Certificate No. A27CE issued January 7, 1977. 
 
Production Basis:  
Production Certificate No. 312.  Effective February 15, 1985, and on, Production Certificate No. 4 is applicable to all spares 
production. See NOTE 8 for specific effectivity of P.C. 4 on new airplane serials. 
 
Equipment:   
The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed 
in the aircraft for certification. 
 
NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and 
loading instructions when necessary must be provided for each aircraft at the time of original certification.  
 
 The certificated empty weight and corresponding center of gravity location must include:  
 
  Unusable fuel  58.0 lb. at +247.0 in.  (S/N 501-0001 and on) 
    52.8 lb. at +298.4 in.  (S/N 551-0001 and on) 
  Undrainable oil   3.0 lb. at +322.0 in.  (501-0001 and on) 
     3.0 lb. at +367.0 in.  (551-0001 and on) 
  Hydraulic fluid   27.5 lb. at +284.0 in.  (501-0001 and on) 
     30.5 lb. at +322.0 in.  (551-0001 and on) 
 
NOTE 2. The aircraft must be operated according to the FAA Approved Airplane Flight Manual.  Required placards 
are listed on Cessna Drawing 5500000 and 5400100 for the Model 501, and 6500000 and 6401000 for the 
Model 551, and are also included in Chapter 11 of the Airplane Maintenance Manual. 
 
NOTE 3. See Maintenance Manual, Chapter 4, "Airworthiness Limitations" for component mandatory retirement life 
information. 
 
NOTE 4. All replacement seats (crew and passenger), although they may comply with TSO C39, must also be 
demonstrated to comply with FAR 25.785. 
 
NOTE 5. Deleted. 
 
NOTE 6. Aircraft conforming to ECR EC04139 are eligible for 9,500 lb. zero fuel weight with VMO reduced to 260 
KCAS from 14,000 ft. to 30,500 ft.  (Model 501) 
 
 Model 551, S/N 551-0001 through 551-0549, conforming to ECR EC04574 are eligible for 11,000 lb. zero 
fuel weight with VMO reduced to 260 KCAS from 14,000 ft. to 30,500 ft. 11,000 lb. zero fuel weight   
  provision is standard at S/N 551-0550 and up. 
 
NOTE 7. Approved nose tires are limited to those listed in the Limitations Section of the Airplane Flight Manual.  
 
NOTE 8. Production Certificate No. 4 effective at Serial 501-0687 and on. 
 
NOTE 9. Equipment installations or other modifications to the tailcone area must be coordinated with the Wichita 
Aircraft Certification Office.

A27CE 8 Rev. 18 
 
Data Pertinent to All Models  (cont’d) 
 
NOTE 10. For the Model 501, the basic unit number and the serial number may not coincide until unit number 675  
 (S/N 501-0675).  Contact Cessna Customer Service regarding Model 501 unit number and airplane serial 
number effectivity. 
 
NOTE 11. For the Model 551, the basic unit number and serial number may not coincide until unit number 445 (S/N 
551-0445).  Contact Cessna Customer Service regarding Model 551 unit number and airplane serial number 
effectivity.  
 
NOTE 12. Certain Models meet the initial airworthiness requirements for operation in Reduced Vertical Separation 
Minimum (RSVM) airspace. 
 
 Model 501 Citation Unit Numbers 501-0275 through 501-0689 that have accomplished Cessna Service 
Bulletin SB500-34-65. 
   
 Model 551 Citation II Unit Numbers 551-0002 through 551-0733 that have accomplished Cessna Service 
Bulletin SB 550-34-79. 
 
 Each operator must obtain RVSM operating approval directly from the FAA. 
 
NOTE 13. Per Cessna Service Bulletin SB72-2, a JT15D-1B used in combination with a JT15D-1A is required to be 
operated to JT15D-1A engine limitations. 
 
 
--- END ---
```

## ADs (19, in force first)

- [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2015-17-12](https://openairdocs.org/ad/2015-17-12): Air conditioning · Freon air conditioning system (Textron STC SA3849SW or 3 others). Effective Sep 29, 2015
- [AD 2013-09-11](https://openairdocs.org/ad/2013-09-11): Air Conditioning · Cessna 500, 501, 550 and 5 more. Effective Jul 5, 2013
- [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008
- [AD 2007-11-17](https://openairdocs.org/ad/2007-11-17): Wires for the positive and negative terminal studs of the engine and/or auxiliary power unit (APU) fire extinguishing bottles. · Cessna 500, 501, 550 and 5 more. Effective Jul 6, 2007
- [AD 2006-06-03](https://openairdocs.org/ad/2006-06-03): Airplane flight manual (AFM) · Cessna 500, 501, 550 and 3 more. Effective Apr 20, 2006
- [AD 2004-08-15](https://openairdocs.org/ad/2004-08-15): TAWS8000 terrain awareness warning systems (TAWS) · Cessna 421, 500, 501 and 18 more. Effective Jun 7, 2004
- [AD 2004-09-05](https://openairdocs.org/ad/2004-09-05): Brake Stator Disks · Cessna 500, 501, 550 and 1 more. Effective Jun 2, 2004
- [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 2001-22-14](https://openairdocs.org/ad/2001-22-14): Fire Extinguishing System Bottle Cartridges · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 105 more. Effective Dec 10, 2001
- [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998
- [AD 98-04-38](https://openairdocs.org/ad/98-04-38): AFM - Limitations Section - Icing · Cessna 500, 501, 550 and 2 more. Effective Mar 25, 1998
- [AD 93-05-15](https://openairdocs.org/ad/93-05-15): Thrust Reverser Throttle Load Limiter · Cessna 500, 501, 550 and 4 more. Effective Apr 23, 1993
- [AD 90-07-10 R1](https://openairdocs.org/ad/90-07-10-R1): Air Conditioning System · Cessna 550, 551 and S550 with STC SA2698SW. Effective May 29, 1990
- [AD 90-06-13](https://openairdocs.org/ad/90-06-13): Vertical Gyro · Bombardier DHC-8-101, DHC-8-102, DHC-8-103 and 14 more. Effective Mar 30, 1990
- [AD 89-16-10](https://openairdocs.org/ad/89-16-10): Fuel Flow Transmitter · Cessna 550 and 551. Effective Sep 7, 1989
- [AD 80-09-09](https://openairdocs.org/ad/80-09-09): Dual Flight Director Installation · Cessna 500, 501, 550 and 1 more. Effective May 12, 1980
- [AD 79-12-06](https://openairdocs.org/ad/79-12-06): Upper & Lower Spar Cap Stems · Cessna 500, 501, 550 and 1 more. Effective Apr 10, 1980

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna 501](https://openairdocs.org/model/cessna-501): 189 aircraft (registry code 2076603)
- [Cessna 551](https://openairdocs.org/model/cessna-551): 34 aircraft (registry code 2076605)

## STCs approved under this data sheet (199, first 50)

- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA12345IB](https://openairdocs.org/stc/SA12345IB): Replacement of the Halon Type 1211 portable fire extinguisher with the Halotron BrX portable fire extinguisher. Cessna Duesseldorf Citation Service Center GmbH
- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC SA02017WI](https://openairdocs.org/stc/SA02017WI): The Installation of the Parker-Meggitt iPRESS™ System. 3S Certification LLC
- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica
Cellular Module (avCM. Aircraft Systems and Manufacturing Inc.
- [STC SA04051CH](https://openairdocs.org/stc/SA04051CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC
- [STC ST02432LA](https://openairdocs.org/stc/ST02432LA): Installation of Dual Garmin GTN 6XX/7XX Series Global Navigation System with Structural Antenna and WAAS approval; Garmin GMA 35 Audio Panel; Dual Garmin GTX 33 Mode S Transponders; Garmin GWX 70 Weather Radar; and Garmin GDL-88 ADS-B Transceiver on airplane models with a SPZ-500AFCS. JETTECH LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA2005SO](https://openairdocs.org/stc/SA2005SO): Installation of a third stand-by attitude gyro and dedicated power supply AIM P/N  PE  24-1RM. Summit Aviation Inc
- [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics
- [STC ST00011WI](https://openairdocs.org/stc/ST00011WI): Installation of Concorde RG380E/40 and 40B battery.. Aero-Mach Wilco LLC
- [STC SA1298GL](https://openairdocs.org/stc/SA1298GL): Installation of Cleveland main wheels and brakes.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA883GL](https://openairdocs.org/stc/SA883GL): Install aircraft wheel and brake conversion kit 199-137.. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA02220AK](https://openairdocs.org/stc/SA02220AK): Installation of Genesys Aerosystems, Inc. FlightLogic Electronic Flight Instrument System (EFIS) in accordance with Genesys Aerosystems, Inc., System Installation Manual Commuter and Large Aircraft, Document Number 150-045057, Revision M, dated August 13, 2014, or later FAA approved revisions.. Genesys Aerosystems Inc.
- [STC SA02273SE](https://openairdocs.org/stc/SA02273SE): Installation of a Crane Aerospace & Electronics Tire Sensor Assembly. ELDEC Corporation
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [STC SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC
- [STC SA8458SW](https://openairdocs.org/stc/SA8458SW): Installation of quick release nose radome latch mechanisms.. Sierra Industries Ltd.
- [STC SA01156WI](https://openairdocs.org/stc/SA01156WI): Installation of IS&S Air Data System with Reduced Vertical Separation Minimum (RVSM) compliant Dual Air Data System.. Blackhawk Aerospace Technologies Inc.
- [STC SA01196WI](https://openairdocs.org/stc/SA01196WI): Installation of  Universal Avionics EFI-550 2-Display EFIS System.  Data required: (1) Columbia Avionics, Inc. Master Document List No. 30141145, Revision 3, dated September 24, 2003; and (2) FAA Approved Flight Manual Supplement 30141160, dated September 30, 2003, or later FAA Approved Revisions to (1) or (2).. Blackhawk Aerospace Technologies Inc.
- [STC SA01469WI](https://openairdocs.org/stc/SA01469WI): Installation of Universal Avionics EFI-890R Flat Panel EFIS System. Blackhawk Aerospace Technologies Inc.
- [STC SA01697WI](https://openairdocs.org/stc/SA01697WI): Installation of Garmin GTN Series GPS/Comm/Nav Systems with optional Garmin GDL-69/A XM Weather Data Link, GTX-33 Series Transponders and optional Bendix/King KMR-675 Marker Beacon Receiver.. Blackhawk Aerospace Technologies Inc.
- [STC ST00662WI](https://openairdocs.org/stc/ST00662WI): Installation of Bendix/King EFS-50 Two-Tube (EFIS) Electronic Flight Instrumentation System.. Blackhawk Aerospace Technologies Inc.
- [STC ST01162WI](https://openairdocs.org/stc/ST01162WI): Reduced Vertical Separation Minimum (RVSM) group airworthiness approval of  the Cessna Aircraft Model 500, 501, 550 and 551.. Blackhawk Aerospace Technologies Inc.
- [STC ST02989AT](https://openairdocs.org/stc/ST02989AT): Installation of a modified Glareshield.. Continental Aerospace Technologies Inc
- [STC SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc.
- [STC ST02642AT](https://openairdocs.org/stc/ST02642AT): Installation of a RVSM Air Data System. Carlisle Interconnect Technologies Inc.
- [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS
- [STC SA2628NM](https://openairdocs.org/stc/SA2628NM): Optional takeoff gross weight increase. New Flight Corporation
- [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac Inc.
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA01750SE](https://openairdocs.org/stc/SA01750SE): Fabrication and Installation of Dahlia Doubler. Fliegen Works Inc.
- [STC SA01751SE](https://openairdocs.org/stc/SA01751SE): Fabrication and Installation of Panida Doubler. Fliegen Works Inc.
- [STC SA01752SE](https://openairdocs.org/stc/SA01752SE): Fabrication and Installation of Panida Doubler.. Fliegen Works Inc.
- [STC SA2698SW](https://openairdocs.org/stc/SA2698SW): Installation of freon air conditioning system.. Air Comm Corporation
- [STC SA2916SW](https://openairdocs.org/stc/SA2916SW): Installation of alternate gear horn switch.. Air Comm Corporation
- [STC SA04176NY](https://openairdocs.org/stc/SA04176NY): Installation of Cabin Entry Step Assembly. Skyway Group Inc
- [STC SA00153SE](https://openairdocs.org/stc/SA00153SE): Installation of emergency medical stretcher, oxygen, and electrical systems.. LifePort LLC
- [STC ST01898WI](https://openairdocs.org/stc/ST01898WI): Installation of the RVSM capable Garmin G600 with GDU-1060 Touch Screen Primary Flight Display (PFD). JETTECH LLC
- [STC SA732NW](https://openairdocs.org/stc/SA732NW): Installation of Eagle SP performance system, including recontoured wing leading edge, wing tip extension, increased gross weight, increased fuel capacity, and other minor refinements.. Innova Aerospace Service & Support LLC
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA03973NY](https://openairdocs.org/stc/SA03973NY): Replacement of existing TCAS 7.0 by TCAS 7.1. Scandinavian Avionics Design ApS
- [STC ST00276WI](https://openairdocs.org/stc/ST00276WI): Installation of Kedeg Company 21BC11e Coaleser Assemly.. Purolator Facet, Inc
- [STC ST00366WI](https://openairdocs.org/stc/ST00366WI): Installation of Keddeg Company P/N 21BC115 Coalescer Assembly. Purolator Facet, Inc
- [STC SA00461WI](https://openairdocs.org/stc/SA00461WI): Installation of an AlliedSignal CAS 66A Traffic and Collision Avoidance System I (TCAS I). Textron Aviation Inc
- [STC SA11050SC-D](https://openairdocs.org/stc/SA11050SC-D): Installation of Optional Engine Indicating System (EIS). Sierra Industries Ltd.
- [STC SA152RM](https://openairdocs.org/stc/SA152RM): Installation of extended range fuel tank and relocation of aft pressure bulkhead.. Sierra Industries Inc

All 199: https://openairdocs.org/tcds/A27CE/stcs.md

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